Systems and techniques for launching a payload

ABSTRACT

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

RELATED APPLICATIONS

This application claims priority to U.S. Provisional Application No.62/703,866, filed Jul. 26, 2018, which is incorporated herein byreference.

BACKGROUND

Traditional aerospace launch technologies use multi-stage chemicalrockets, typically lifting from the surface (or near-surface) of aplanet or moon, starting with nearly zero relative velocity. The rocketequation predicts that a very small payload fraction to space isallowable 1-10% or smaller compared with takeoff gross weight ofconventional launch vehicle. While offering modest quasi-staticacceleration loads to the payloads (3-10 G's) in very low frequencyrange and modest to high shock acceleration in high frequency range forpyro events (e.g., spacecraft separation rings and bolts, stagingseparation, etc.). These traditional rocket loads and dynamics arecompatible with existing fragile spacecraft as well as compatible withhuman spaceflight. The first stages of these conventional rockets departslowly and perform gravity turns that are very costly from a performancestandpoint. The vehicles must carry all of its fuel and oxidizer with itduring the entire flight ultimately leaving the payload with the desiredenergy state (delta v) required for a specific space mission. As such,there is a need to address some or all of these limitations.

SUMMARY

This disclosure describes various techniques and systems for rapidlow-cost access to suborbital and orbital space and accommodation ofacceleration of sensitive payloads to space. For example, a distributedgas injection system may be used in a ram accelerator to launch multiplepayloads through the atmosphere. Additionally or alternatively, multipleprojectiles may assemble during flight through the atmosphere totransfer and/or resources to another projectile.

BRIEF DESCRIPTION OF THE DRAWINGS

The Detailed Description is set forth with reference to the accompanyingfigures. In the figures, the left-most digit(s) of a reference numberidentifies the figure in which the reference number first appears. Thesame reference numbers in different figures indicate similar oridentical items.

FIG. 1 shows an illustrative ram accelerator.

FIG. 2 shows an illustrative ram accelerator acceleration profile.

FIGS. 3-5 show illustrative launch configurations.

FIG. 6 shows an illustrative launch system.

FIG. 7 shows an illustrative projectile.

FIGS. 8A-10 illustrative launch system configurations.

FIGS. 11A-B shows an illustrative projectile support system.

FIG. 12 shows an illustrative launch locking mechanism.

FIGS. 13 and 14 show illustrative launching techniques.

FIGS. 15 and 16 show illustrative projectile.

FIG. 17 shows an illustrative ball valve.

FIGS. 18A-D shows an illustrative launch platform.

FIG. 19 shows an illustrative kinetic launch system.

FIG. 20 shows an illustrative launch system with an illustrativeprojectile.

DETAILED DESCRIPTION Overview

This disclosure describes various techniques and systems for rapidlow-cost access to suborbital and orbital space and accommodation ofacceleration of sensitive payloads to space.

An internet connected system allows a user to select a pre-packagedsatellite or payload or electronic and upload specific code on demandand launch or place their own payloads on board and market and promotetheir own space business and launch on demand. Additionally oralternatively, various embodiments contemplate systems and techniquesfor launching multiple launch vehicles separately and having themassemble in flight. Additionally or alternatively, various embodimentscontemplate a relatively low G-load launch system allowing a projectileto accelerate at relatively lower G-loads.

Traditional aerospace launch technologies use multi-stage chemicalrockets, typically lifting from the surface (or near-surface) of aplanet or moon, starting with nearly zero relative velocity. The rocketequation predicts that a very small payload fraction to space isallowable 1-10% or smaller compared with takeoff gross weight ofconventional launch vehicle. While offering modest quasi-staticacceleration loads to the payloads (3-10 G's) in very low frequencyrange and modest to high shock acceleration in high frequency range forpyro events (e.g., spacecraft separation rings and bolts, stagingseparation, etc.). These traditional rocket loads and dynamics arecompatible with existing fragile spacecraft as well as compatible withhuman spaceflight. The first stages of these conventional rockets departslowly and perform gravity turns that are very costly from a performancestandpoint. The vehicles must carry all of its fuel and oxidizer with itduring the entire flight ultimately leaving the payload with the desiredenergy state (delta v) required for a specific space mission. Typicaldelta v for orbital flight is approximately 7.5 km/s. These traditionalrocket systems are high capital expense systems, high operating expenseand limited re-usability for one or more stages for conventional rocketswith vertical or horizontal landing systems. Since the days Jules Verne,gun launch spacecraft have been considered as an alternative totraditional spaceflight. Unfortunately, guns do not scale well forlarger masses to high velocity, leading to very long barrels (for guns)and limited performance and extremely large acceleration loads on theprojectiles and payloads. High acceleration compatible electronics havebeen shown to survive military and scientific gun launch, however thismethod is incompatible with acceleration “G” loads that are typical fortraditional space payloads as well as human spaceflight.

This application discloses systems and techniques for repetitivelow-cost launches to sub-orbital, orbital, and earth escape velocitylaunches to space while providing a modest acceleration load profile forthe payload and projectile in all stages of flight from start up toorbital insertion. These various novel embodiments use one or moreacceleration systems, for example, ram accelerator systems with a lowacceleration start “gun” (Electromagnet Rail gun, coil gun, or vented orunvented light gas gun and distributed injection cold and hot gas guns)to bring the projectile(s) up to ram or baffle tube ram acceleratorstart speed.

Additionally or alternatively, while a ram accelerator is discussed inthis application, it is intended that additional launch systems may beused in addition to or in lieu of a ram accelerator. For example, animpulse launch system may be used, including, but not limited to acentripetal, centrifugal, centrifical, rotating, spinning, catapultlaunch systems, or other mechanical or gas dynamic or electricalpropulsion system, for combinations thereof, to launch one or moreprojectiles.

FIG. 1 shows an illustrative ram accelerator system 100. Ramaccelerators and baffle tube ram accelerators are often classified aschemical mass drivers that accelerate a projectile through a tube filledwith combustible chemicals setting up a ramjet engine effect using anormal shock on the back base to accelerate the projectiles through thegases. For example, FIG. 1 shows a ram accelerator system 100 with a ramaccelerator section 102 and a starting system 104. For example, thestarting system 104 may comprise a cold gas gun starter. FIG. 1 alsoshows a projectile assembly 106. For example, the projectile assembly106 may comprise a projectile 108 and an obturator 110. FIG. 1 alsoshows a gas valve 112 disposed at the starting system 104 to introduce apropellant to accelerate the projectile assembly 106. FIG. 1 also showsa first stage 114 of the ram accelerator section 102. Variousembodiments contemplate that various stages of the ram acceleratorsection 102 may be isolated by transitions (e.g., transition 116) andsupplied with propellant gasses through supply mechanisms (e.g., supplyvalve 118). Various embodiments contemplate that transition 116 maycomprise a diaphragm, a valve, an electromagnetic device, or anequalized pressure, among other configurations. FIG. 1 also shows asecond stage 120 through which the projectile may pass. Variousembodiments contemplate the projectile sustaining a shock wave throughthe second stage 120 while the second stage 120 is pressurized with adesired media combusting the same to further accelerate the projectile.

Additionally or alternatively the ram accelerator section 102 mayfurther comprise any number of stages. The number of stages is based ona desired launch profile, acceleration profile, jerk profile, amongother factors. Additionally or alternatively, FIG. 1 also shows a thirdstage 122. The third stage 122 may be configured similarly to the secondstage 120 to further accelerate the projectile. However, the third stage122 may also be configured to transition the pressure that theprojectile experiences in earlier stages to a pressure more desirable orentering the atmosphere at exit 124. Various embodiments contemplatethat this may cause a deceleration in the projectile from the precedingstage, however, by beginning to equalize the pressure with theatmosphere in a controlled manner the projectile may experience lessshock at the transition to the atmosphere at exit 124 and overallincrease the overall performance and/or desirable flight conditionsthrough the atmosphere.

Additionally or alternatively, various embodiments contemplate that aRam-jet may operate differently than a gun, in that it allows for acustomized pressure and propellant types that vary in discrete “stages”or in a continuum gradient and thus allow a custom-tailored accelerationprofile for the projectile assembly. This offers a unique impulse spacelaunch capability that due to variable length and G-loads allowsconventional low-G tolerant payloads a direct ride to hypervelocityimpulse space launch without the significantly larger G-shock loading ofa large gun.

Additionally or alternatively, various embodiments contemplate that aprojectile with an obturator or contact through an obturator typicallytransfers a pressure load from the start gun through the projectilebringing it up to ram acceleration speeds. Various embodimentscontemplate a typical speed of 600 m/s for a baffle tube ram acceleratorsystem and 850-1100 m/s for a smooth bore or railed ram acceleratorsystem. After the projectile reaches “ramming” effective speeds, the ramaccelerator or baffle tube ram accelerator may have multiple gas stagesto tailor the acceleration profile of the projectile assembly to reachthe desired exit velocity.

Additionally or alternatively, various embodiments contemplate that theprojectile shape along with a number of factors are tailorable to impactthe effectiveness of the system. For example, a number of those factorsinclude, but are not limited to, velocity in the tube, variable gaspressure, types, density, and locations of propellants, projectile mass,payload mass, center of gravity (CG), maximum diameter, combustionadditives inhibitors, obturators, tube structure, stage separationmechanisms such as, but not limited to slow ball valves, fast ballvalves, knife-gate valves, diaphragms, rails, projectile fin interactionamong others and combinations thereof.

FIG. 2 shows an illustrative example 200 of tailoring sections of a ramaccelerator (102, 104, and 106) with a pressure, medium, transitionfeatures among others, to control the Mach number and thrust produced toincrease the velocity.

Various embodiments contemplate a start gun configured to enable a low Gram operation. A pressure or an electromagnetic field may to act uponthe projectile assembly to accelerate the projectile to ram startvelocity. For example, in one embodiment a single stage or 2-stage lightgas gun may be used to generate a modest pressure to move a projectile.For example, a 2 kg (4.41 lb) projectile with bore diameter of 100 mm(˜4 inches) of the launch tube (and ram accelerator tube) with 6.894 MPa(1000 psia) will experience an acceleration of approximately 27100m/s{circumflex over ( )}2 which equates to 2740 G's peak. Which,depending on the sound speed of the gas (for example, He, H2, N2, air,among others) used for the gun, will accelerate the projectile up toramming speeds over a known distance. The lower the G-load allowable,the longer the gun, up to appoint where normal smooth and rail tube boreram acceleration may not be able to “start” and thus a lower entrancevelocity accelerator call the baffle tube ram accelerator may be used.As another example a 1500 kg (2200 lb) projectile assembly with a 1.5meter inner diameter needs only 275 kPa (40 psi) pressure to move aprojectile at 325 m/s{circumflex over ( )}2 (33 G's) initialacceleration. However, an added volume of gas mass at contact pressuremay be introduced to offer a constant acceleration and reach a desiredstart gun velocity to enter ram acceleration.

Additionally or alternatively, various embodiments contemplate that anaccelerator for the start gun is not a gas gun, but an electromagneticmass driver (e.g., a coil or rail gun) pushing an armature, similar tothe obturator, to the start speeds of the ram accelerator or the baffletube ram accelerator.

Additionally or alternatively, various embodiments contemplate a startgun, vented or not vented, may use a distributed gas injection gun.Various embodiments contemplate injecting cold gas as the projectileassembly passes through a series of fast valves or breaking diaphragmsthat continuously add high pressure mass flow to push the projectile upto ramming speeds or the slow starting baffle tube ramming speeds.

Additionally or alternatively, various embodiments contemplate featuresof a distributed injection system may include but are not limited to:Tube Diameter, Tube Length, Projectile Mass, Pressure of Supply, Volumeof Supply Injection area, Injection area as function of location, speedof sound of gas, density, temperature, type (He, H2, N2, air, etc.),Timing of the injection, Type of Gas, Press in the tube, Friction of theobturator or projectile (seal), among others.

Additionally or alternatively, various embodiments contemplate thatsince the system may use low cost start gun or re-usable start-gun gas,and a baffle tube ram accelerator, they system is able to use a muchlower energy start mechanism, for example, similar to conventionalcatapult launch system the navy uses or simple gas or low fidelityelectric gun solutions for the start gun.

FIG. 3 shows an illustrative example of a tailorable ram acceleratorsystem 300. For example, for a given projectile mass the pressure on theram accelerator projectile is provided by the ram accelerator system(e.g., based at least in part on projectile at speed, velocity, ram tubesize and configuration, and combustion gases).

Additionally or alternatively, various embodiments contemplate that thesystem is able to bound the acceleration in each stage by ProjectileMass, combustion gases, and fill pressure. For example, a projectile of1500 kg in a 1500 mm diameter Ram tube section, a Pressuremultiplication of fill of about 20× fill pressure is expected. For a 2psia (13800 Pa) fill pressure, the system expects to see a lowAcceleration of 33 G's. Each stage may be tailored to maintain a nearcontact acceleration and the superposition of all of these stages andthe acceleration may be a nearly constant acceleration profile.

Additionally or alternatively, various embodiments contemplate anacceleration system in a vertical or inclined orientation for theprojectile to exit the system, for example, to be directed to space.However, the orientation may be in any direction. For example, variousembodiments contemplate additional orientations. For example, variousembodiments contemplate orientating the projectile exit path to besubstantially horizontal or substantially parallel to a direction ofmovement of an aircraft or surface based vehicle. For example, anembodiment of a launch system may be mounted to or installed in anaircraft, for example, a commercial, military, private, or research, inflight. Additionally or alternatively, various embodiments contemplateorientating the projectile path in any direction for impact uses, forexample, tunneling or drilling. Additionally, the orientation may bedownwards, for example, for drilling or shaft making.

Additionally or alternatively, various embodiments contemplate aG-matched distributed injection gas gun coupled into a nearly constant Gram accelerator system providing a tailored G load for the accelerationportion of flight. Additionally or alternatively, various embodimentscontemplate integrating a distributed injection gas gun with a movablediaphragm for example, a cup shaped device, configured to increase therelative velocity of the projectile in a medium, for example the gas ofthe gas gun. Additionally or alternatively, the distributed injectiongas gun may comprise the use of valves, highspeed valves, baffles, orcombinations thereof of to selectively inject gas into start gun.

Additionally or alternatively, various embodiments contemplate managingG loads for the jerk (rate of change of acceleration/deceleration) andacceleration (deceleration) between stages and at or near the exit. Forexample, use of slow valves as stage separation, allows for constantpressure fill between the stages. For example, just prior to startingthe start gun, the stages are brought into equal pressure with apressure measurement and tailoring system during fill or with purge ofeach stage of gas to have nearly exact gauge pressure between stages.The valves, when open, allow only diffusion or else a prescribed aboutof mixing between the stages, creating a transition zone for theprojectile to softly pass through rather than having a sharpacceleration change at each stage transition. Additionally oralternatively, various embodiments contemplate that each stage of theram may be monitored for pressure and small differential pressure device(regulator) may manage the valves.

Additionally or alternatively, various embodiments contemplate that aFast Valve operation may allow the system to fill each stage atdifferent pressure and just prior to the arrival of the projectile tothe stage a diaphragm is broken or a high speed valve is actuated toallow the incoming projectile to maintain a nearly constant accelerationbetween stages as the different pressures of the adjoining stages may bea necessary variable to maintain constant and/or consistent accelerationof the projectile.

Additionally or alternatively, various embodiments contemplate usingelectromagnetics (e.g., coilgun, rail gun, etc.) to transfer loads froma coil (for instance) wrapped around a portion of the Ram tube(non-ferrous or ferrous) to the projectile where that magnetic fieldinteracts with a ferrous or other magnet field within the projectileassembly (e.g., obturator, armature, body, projectile, etc.). With thismechanism, the system is able to manage a transition between stageswhere there is a discontinuity in between the stages and theelectromagnetic field can be used just ahead of the arrival of theprojectile to synch up and match the acceleration profile and maintainover a short distance the constant acceleration as the projectiletransitions into the next stage of the accelerator.

At the tube exit into the atmosphere there will be a relativelyhigh-drag portion of the flight. To reduce this effect, variousembodiments contemplate that the system may use variable gas dynamics totransition from a ram acceleration mode and transition into coast modewith modest deceleration, while maintaining an acceptable exit velocity.For example, near the exit of the ram accelerator, the system can usevariable sound speed gases and thinner combustion mixtures to transitionto a low to no acceleration from the modest G load acceleration. Heatingair in the tube as well as evacuation section of a drift tube andheating the atmosphere ahead of the projectile are all methods thevarying the acceleration of the projectile to have a soft transitioninto the higher drag portion of flight cause by the atmosphere.

Additionally or alternatively, various embodiments contemplate thatreleasing the projectile at the top of a high-altitude mountain or froman aircraft in lower density air or off into a planet or a moon withlittle to no atmosphere are ways to reduce the atmospheric drag thatwould otherwise decelerate the payload.

Additionally or alternatively, various embodiments contemplate that thediscussed techniques and systems not only tailor the G-load(acceleration and deceleration) but also tailor the rate of change ofthe deceleration/acceleration: the jerk. For some payloads, includinghuman astronauts and pilots/passengers, may be a primary loading problemthat may result in damage. Managing the Jerk as well as the accelerationis critical to successful payload acceleration management.

For example, a 2 kg, 75 mm frontal diameter projectile launched from a100 mm tube released into the atmosphere sees a constant deceleration ofabout 139 G's during atmospheric coast transit. However, a 1500 kg, 1125mm projectile frontal diameter from a 1500 mm tube see about 42 G's ofdeceleration. These acceleration loads in the transition zones and theexit are important to manage and various embodiments of the system canafford a tailored acceleration profile from end to end to ensure thepayload is not exposed to detrimental forces, pressures, accelerationand jerks during the impulse launch and coast sequence.

Illustrative User Experience

The following is a description of illustrative user experiences andpaths of the projectile throughout several embodiments of the system.

For example, various embodiments contemplate a user (human orautomated/robotic user) is able to select and order a Payload Modulefrom a remote location, for example, a website, through an application,through an online store or directly pay at a kiosk or vending machine.The user may use their hand held mobile device, laptop or internetenable computing device or telephone or in-person.

Additionally or alternatively, various embodiments contemplate that atreceipt of payment, the fulfillment system will manufacture (e.g., 3Dprint, or conventional metallic and/or composite manufacturing methods)to order a custom payload module or dispense a pre-made payload module.In one embodiment, the payload module consists of a metallic orcomposite tube, optionally threaded on one or both ends. A lower end capprovided a bottom to the payload module with a diameter and a surfacethe interfaces to an aero stabilizing system and transfer loads duringthe launch and ram acceleration sequence underground to accelerate boththe projectile assembly with payload module and the aeroshell.

Additionally or alternatively, various embodiments contemplate that thepayload module is marked with Serial # or RFID, etc. Additionally oralternatively, various embodiments contemplate that the vending machine,kiosk, etc. provides atmospheric conditioning to the payload system.

Additionally or alternatively, various embodiments contemplate a usermay enter a Punch Code into Vending Machine which will dispense PayloadModule. Additionally or alternatively, the user may order it online. Theuser may place a desired product or products into the payload module.The user may send the Module back to system, where the system mayassemble the projectile assembly with the payload module. For example,the payload may be coupled to a nose cone as well as an aeroshell.Additionally or alternatively, various embodiments contemplate that theassembled projectile assembly is loaded into the machine.

Additionally or alternatively, various embodiments contemplate that theprojectile and the payload module are separate and are displayed inseparate locations (in the vending machine) or in separate machines. TheProjectile assembly and the payload module may come together andself-assemble automatically at the surface or underground. This allowsthe user to always see and interact, for example, via online, with thepayload or physically with the payload in the payload processing unit.The vending machine may be a big as shipping container or a buildingdepending on number of payloads, projectile assemblies and sizes(diameter, length, mass). Various embodiments of the system allows theuser to show off, market, test, check and generally interact andcommunicate upload software, etc. before final joining with theprojectile assembly.

Additionally or alternatively, various embodiments contemplate a remotelaunch capability within a window, rather than a specific count down.Additionally or alternatively, the system may provide a remote launchsafety key encrypted via the internet. Additionally or alternatively,various embodiments contemplate a remote filling of the ram acceleratorsystem.

Various embodiments contemplate that the system may use a cold gas gunor a light gas gun filling in one or more breaches that operate atmodest pressure offer low G load launch for start gun and enterprojectile assembly into the ram accelerator, which may be configured asa smooth bore, baffle tube, railed, among others, or combinationsthereof.

FIG. 3 shows an illustrative embodiment of a launch environment 300. Forexample FIG. 3 shows an illustrative launch system 302 coupled to adistribution device 304 configured to select and load a projectile 306into the launch system 302. After the system launches the projectile306, the projectile 306 may travel on a ballistic trajectory. Variousembodiments contemplate a second stage 308, for example an ATV,continuing to fly while the first stage portion 310 of the projectile306 may be detached from the second stage 308. Various embodimentscontemplate recovering the first stage portion 310 after detachment.Additionally or alternatively, the second stage 308 may deploy apropulsion system to further boost its flight. For example, the secondstage 308 may perform an orbital insertion burn. Additionally oralternatively, various embodiments contemplate the second stage 308deploying a cargo 312, for example, a satellite. Additionally oralternatively, portions of the second stage 308 may stay in orbit or maydeorbit, for example, as portions 314. Various embodiments contemplatethat depending on the mission profile and construction and composition,portions 314 may burn up in the atmosphere or be recovered on theground. Additionally or alternatively, portions 314 may have control andpropulsion systems to actively guide and control a landing, a deorbit,or similar maneuvers.

Additionally or alternatively, various embodiments contemplate anelectro-magnetic release of the locking cup or shearing of locking ringand O-ring. For example, the projectile may have an O-ring as well as ashear spring lip for single ended operation of a projectile. Anillustrative example includes a 100 mm diameter projectile. Thisprojectile may be machined from a single rod of grey PVC. This lock ringmay be split into 3 parts. A secondary lip may be included and may beused as an intended shear mechanism. Additionally, an obturator with anO-ring 0.92 inches from the back of the obturator may be used. TheO-ring may comprise various materials, for example, a 2-239 buna O-ring.The O-ring groove may be 0.187 inches wide and 0.101 inches deep. Thelock ring may be machined from 4″ schedule 80 grey PVC pipe withthickness of 0.15 inches. The width may be 0.373 inches. Additionally, aspacer material, for example, weather stripping, may be cut into 0.18inches thick pieces and may be installed approximately every 20 degreesaround the circumference of the lock ring. The lock ring groove may be0.385 inches wide and 0.225 inches deep. The shear lip may be positionedbehind the lock ring, and may be 0.35 inches thick.

This configuration is an illustrative example of how the system allowsoperation in variable pressure G-loading rather than high pressure ordetonation. For example, the O-ring may maintain the pressure of thebreak to push projectile assembly. Additionally, the pressure may alsoovercome the shear ring. Here, the O-ring could be used in a case wherethe section is variable and the O-ring holds in shear and pressure aswell. For example, the section may form a horn-like shape.

Additionally or alternatively, various embodiments contemplate G-load(acceleration) conditioning of the payload and the projectile assemblyduring the entire launch sequence and low G (low Jerk, modestacceleration handling) during all stage transitions including enteringthe atmosphere and introducing the system to atmospheric drag.

Additionally or alternatively, various embodiments contemplate aseparation sequence of the payload assembly system allowing anatmospheric transit vehicle (ATV) to emerge. For example, the payloadassembly system may include the payload, obturator, aeroshell, and insome embodiments stages, where the obturator, and, in some embodiments,stages, fall away and the payload coupled to an aerodynamicstabilization component may emerge. For example, the aerodynamicstabilization component may comprise a telescoping feature adapted tofins which may resemble a ballistic dart.

Additionally or alternatively, various embodiments contemplate a dampingmechanism in the separating projectile assembly to ease transition ofpayload into stable atmospheric flight. For example, aerodynamicstabilization component may comprise a telescoping, extensible aerostructure, which may include a rope or cord or tube among others, orcombinations thereof. Additionally or alternatively, an aero structurecould be coupled to the end of the extensible component distal from theend coupled to the payload. The aero structure may comprise fins forstability or drogue chute or ballute or an inflating beam forstabilization, among others, or combinations thereof. Additionally oralternatively, various embodiments contemplate using control rockets tocontrol the atmospheric transit vehicle as augmentative control or fortotal control. Additionally or alternatively, various embodimentscontemplate imparting a rotation (e.g., ballistic spinning) to be usedfor stability.

Additionally or alternatively, various embodiments contemplate that thepayload and any propulsion system and aerodynamics continues to altitudeand inserts into orbit with an insertion burn or return to earth viaballistic trajectory.

Additionally or alternatively, various embodiments contemplate thepayload is encapsulated in a supportive structure, for example, anegg-crate structure, for load transfer and ease of acceleration and jerkand transmission and distribution of those loads. Additionally oralternatively, various embodiments contemplate a variable density liquidballast may be integrated into the ATV to provide support to theinternal structures and components as well as provide ballast to improveatmospheric transition characteristics. This liquid ballast may, in someembodiments, used for thermal sinking and or a source of liquid spraycooling directed via pumping mechanism (mechanical, gravity, thermal,pressure, etc) to cool high heat section of the atmospheric transitvehicle (e.g., a nose cone spray cooling). The ballast fluid (or solidmelted paraffin) at pressure may also be used as TVC (Thrust VectorControl) as liquid control jets using mass flow and pressure injectionthrough, for example the side wall locations of the ATV providinglateral and axial control of the vehicle in the Ram accelerator tube, inthe atmospheric transit as well as potential in-space (high altitude).For example, an ATV carrying solid propulsion or liquid rocket tankseffectively would have experience lower loads via buoyancy in thevariable density liquid ballast. For example, the density of the liquidballast may be selected to provide a neutral buoyancy, a negativebuoyancy, or a positive buoyancy to the internal structure as desired.Additionally or alternatively, the support provided by the liquidballast or the egg-crate structure to the internal components may enablea more efficient design of the internal components. For example, aliquid fuel tank may have a wall thickness sized for a pressure of thetank. However, the thickness of the tank may need to be increasedwithstand the additional loads and stresses caused during the launchprocess. This may add significant weight to the payload to be delivered,for example, to orbit. However, by using the liquid ballast and/or anegg-crate structure to support the tank through the launch process, theincrease to the tank wall thickness may be reduced, minimized, ornegated altogether.

Additionally or alternatively, various embodiments contemplate that at apoint of atmospheric transit completion, a separation mechanism may beactivated to sever some or all of the aeroshell segment(s) to allow foran encapsulated vehicle. The separation mechanism may be shear, tensile,compression failure, or combinations or sequences thereof. The split theATV shell and structure may form the encapsulated payload or orbitalvehicle stages. The separation mechanism may be a linear shaped chargeusing pyrotechnics or could be a high pressure deforming inflatablebladder or tube with a shearing wedge that upon inflation (high pressureshock or slow high pressure) will deform. For example, while deforming,a sharp wedge is translated to shear the aeroshell material (such aswound fiberglass or carbon fiber).

Illustrative Embodiments

Various embodiments contemplate a robust, reusable, Nano and Microsatellite transit vehicle known as the Atmospheric Transfer Vehicle(ATV). However, these techniques and systems are scalable to craft andpayloads much larger than nano and micro satellites. For example, craftcapable of carrying humans as well as larger exploratory or industrialpayloads is also contemplated. Various embodiments contemplateintegrating structural components capable of withstanding an impulsivelaunch from a ram accelerator based launch architectures and in-groundlaunch sites, for example, those based at Spaceport America, near LasCruces N. Mex. This cost-effective launch vehicle enables cheap accessto space, while providing on-demand launches. Along with minor G-loadtoughening of existing cubesat payloads, a new class of tough, low-costpayloads will emerge to be able to be flown on this system. Thereduction of cost and the ability to have on demand launch services willfurther strengthen and accelerate the developing small sat market.

Some of the beneficial innovations in this technology which allow theimpulsive launch include, but are not limited to that the system mayinclude heat resistant aeroshell to help protect payload and upperstages; the system may provide extendable features to allow for stableflight throughout launch; “Egg carton” technology may help distributethe acceleration load throughout the structure; the system also includesan optimized propulsion system; the stages that do not reach orbit maybe recovered for later reuse or disposal; the equipment may be retrievedafterwards by a recovery system that slows the payload and projectileassembly systems to G-loads that allow recovery and recycling or re-usefor next flights; the payload assembly information may be broadcast tothe payload virtual app store for marketing and informationdissemination; the payload may be sent back to the user and originalnose cap return onto the payload cylindrical section; and the system maybe ready for re-use.

Traditional aerospace launch technologies use multi-stage rockets.Lifting from surface of a planet or moon, starting with zero relativevelocity. The Rocket Equation predicts that a very small payloadfraction to space is allowable, for example, 10% or smaller. HighCapital and limited re-usability of one or more stages for conventionalrockets with vertical or horizontal landed systems.

Here, however, various embodiments contemplate use of an automatedpayload processing facility (e.g., vending machine) and integration ofan automated mating above or below ground with the atmospheric transitvehicle (ATV) that is compatible with the Ram accelerator body shape.The ATV may include a sharp nose.

Additionally or alternatively, various embodiments contemplate aninternet of things connection. For example, a user may select a payloadfrom the available options.

Additionally or alternatively, various embodiments contemplate end toend management of the G-loads of the vehicle. For example, the mainlaunch G-loads as well as the active control of vibration of the systemas it transitions from start gas gun interface to launch tube to first,2nd third stage, etc. ram accelerator as well as the exit.

Additionally or alternatively, various embodiments contemplateconditioning the exit of the accelerator. For example, gas atmosphericconditioning, thermal, etc. on the exit of the projectile into theatmosphere may be used to avoid, or reduce, rate of change ofacceleration (jerk) as well as the acceleration conditioning itself.Characteristics of firing may be adjusted to tailor the profile for theexit, for example, to match the outside atmospheric conditions.

Additionally or alternatively, various embodiments contemplate a laserfrom the ground (mirrored, etc) or on board or on the tube to conditionthe air ahead of the projectile as it flies through the atmosphere. Thistechnique may create an artificial thermal/gas induced shape ahead ofthe projectile. This may create cavitation zone where the drag of theoverall system is substantially reduced do to the modest amount ofenergy addition and shaping of the drag.

Additionally or alternatively, various embodiments contemplate that,near the exit of the projectile, the system may heat and push hot air,for example, from a jet from within the tube or just our side the tubeabove or below ground for the exit. This may locally lower the densityof the air as well as changing the sound speed of the gas in the exitportion of the flight to reduce drag, thermal as well as shock, jerk andvibration. Preferably, the system may launch from as high of anelevation as practicable (e.g., a tall mountain, an aircraft, etc.) andhave a relatively low-density atmosphere to enter (e.g., treated ormanipulated as discussed above). The system may operate from awaterborne platform, for example, in the ocean at sea level, or on alake at sea level or at a higher altitude. Water borne application mayallow for ease of pointing (delta V in direction of launch) anddistributed injection integration.

Additionally or alternatively, a soft ride gas spring or electromagneticlauncher, coil gun, may be used to handle and even out the G-loads tospace.

Additionally or alternatively, various embodiments contemplate that thepusher plate (or obturator) used for Ram accelerator “starting” may actas a shock wave mirror.

Additionally or alternatively, various embodiments contemplate that alaser communications system may be used to facilitate operations. Forexample, laser communications have high bandwidth. The system may usethe laser communication technique to offer a service to communicate at ahigh bandwidth between a user or the system and the payloads. Variousembodiments contemplate that the system owner may own the connectionlink to the systems from end to end offering the payload customers anopportunity to use multiple approaches. For example, the user may buy apayload with all the pre-set features of a small satellite that the userwould like, for example, camera(s), processor, IR sensors, releasemechanism, payload bay. Additionally or alternatively, the user mayselect pre-made petri dishes or other media that host life-science andmaterial science applications on-demand.

Illustrative Launch Systems and Techniques

Various embodiments contemplate a multi-barrel launch system. Forexample, a total system cost and payload density ratio compared with Gasmay dictate that heavier payloads for a given area (Ram area) andpropellant mass fraction may be required to have a softer launch (e.g.,lower G-loads). For example, various embodiments contemplate a nominalRam accelerator operating with a fill pressure in the 250 psi to 3000psi range. Additionally or alternatively, various embodimentscontemplate the nominal operation pressure set up by the normal shock(e.g., ring pressure wave) on the aft portion of the ram acceleratorprojectile when in a thermally choked regime and climbing towards thecenter body and nose that pushed the projectile.

Additionally or alternatively, various embodiments contemplateself-assembling atmospheric transit vehicles. For example, one or moreATVs may be launched from multiple barrels of a multi-barrel launchsystem and joint together in flight. For example, after exiting thebarrel or tube, one or more ATVs may be controlled to approach eachother or the one or more ATVs may be launched with a predeterminedintersecting flight path. When sufficiently close to one another, themultiple ATVs may joint together. For example, various embodimentscontemplate using one or more of magnetic connections, lockingconnections, ropes, cables, telescoping connections, nets, mechanicalfasteners (e.g., hook and loop), adhesives (e.g, rapid setting or UVsetting adhesive), among others, or combinations thereof. Additionallyor alternatively, various embodiments contemplate that when connected toeach other, the ATVs may further connect systems of each ATV. Forexample, two or more ATV may connect propellant lines. For example, afirst ATV may be launch with an oxidizer, a second ATV may be launchedwith a fuel, and a third ATV may be launched with an engine. Whenconnected, the first and second ATVs may connect with the third ATVthrough any of the aforementioned techniques. After connection, the ATVsmay then connect propellant lines, for example, such that the fuel andoxidizer from first two ATVs may be fed into the engine of the third ATVto provide thrust.

FIG. 4 shows an illustrative launch system where multiple launchingmechanisms are used to launch multiple projectiles. For example, FIG. 4shows launch environment 400 with a first launch mechanism 402 and asecond launch mechanism 404. Various embodiments contemplate that afirst projectile 406 and a second projectile 408 may be supplied by adistribution system 410. Additionally or alternatively, variousembodiments contemplate at least portions of the first and secondprojectiles 406 and 408 connect in flight to form multiunit ATV 412, forexample, at 414. FIG. 4 also shows a portion of multiunit ATV 412transferring a resource from a portion of the first projectile to aportion of the second projectile, vice versa, or a combination thereof.For example, the portion of the first projectile may transfer apropellant to the portion of the second projectile. Additionally oralternatively, the portion of the second projectile may transfer anenergy (e.g., kinetic energy though, for example, thrust) to the portionof the first projectile, for example, at 416.

Additionally or alternatively, various embodiments contemplate a spacetug configuration. For example, a space tug may grab a hypersonic wireor line, with a damper and a clamp. For example, the space tug may grabon to the ATV from a 1-stage, a 1st stage, or 2nd stage of a launchsystem. The selection of the number of stages and which stage to connectwith may be determined based at least in part on the optimal velocity ofthe relevant components.

Additionally or alternatively, various embodiments contemplate that alaunch tube or series of launch tubes or systems may be bored usinghyper tunnel boring technology and may accommodate a low total cost andspeed of launch vehicle system design.

Additionally or alternatively, various embodiments contemplate allowingthe system to safely launch the people, the fuel and the oxidizer ateffectively different times and under different G load conditions thatare desirable or optimal for each system. For example, the projectile(s)carrying the fuel and or oxidizer could be heavier or launch at higher Gand/or different (e.g., shorter length) tubes when compared to the crewvehicle, so that the vehicles (crew and fuel and oxidizer) can mate upat the point the overall system has linked up. Additionally oralternatively, various embodiments contemplate autochecking the systemsin a short time to allow rapid deployment where the crew capsule may belocked and ready for launch when the rest of the system is prepared fordeployment.

Additionally or alternatively, various embodiments contemplate that tolaunch a low G tolerant payload, the system may capture the drogue leftby one or more ATVs that have launch in different tubes just ahead (andlikely higher G load) of the main capsule which can fly at velocitycomparable to the ATV. Then the ATV with low G tolerant payload isconnected, for example, like connecting a refueling aircraft, to thehigher G ATV, and coasts and then is tugged via normal rocket propulsionof that higher G ATV, for example, a propulsive stage 2 or by aconventional supersonic (subsonic combustion) air breathing ramacceleration.

Additionally or alternatively, various embodiments contemplate the useof a space tether energy generating capability of a space tether tobring energy to a lower ATV after one or more Delta V burns.

Additionally or alternatively, various embodiments contemplatetransferring energy to another ATV, for example, by beaming electricityfrom an ATV to boost lower earth vehicle into higher orbit. Additionallyor alternatively, various embodiments contemplate an array of vehiclesthat beam energy back to an ATV running an electric or hybrid propulsionsystem which can use the energy beamed to it.

Additionally or alternatively, various embodiments contemplateencapsulation of a person or other G-sensitive payload. Here, theG-loads may be managed using the systems and techniques discussed. Forexample, they system may encapsulate the disk aircraft as a capsule. Thecapsule can be smaller like the Manned Orbital Operations SafetyEquipment (MOOSE) developed with the astronaut in the back of theprojectile.

Additionally or alternatively, various embodiments contemplate usingmagnetic connection or physical connection to allow one of more objectsconnected to an accelerating payload. For example, towing an ATV via ramacceleration. For example, reeling out a wire during launch, as forexample, demonstrated by a wire guided TOW missile. Additionally oralternatively, various embodiments contemplate allowing the projectileand obturator (if needed) to connect with a wire or high strength cable,embedded or coiled allowing it to pull something along. The cable mayalso be folded in such away to allow it to connect outside the tube tothe article intended for pulling. That article would have to have a heckof a good damper to deal with G shock loads.

FIG. 5 shows an illustrative launch system where multiple launchingmechanisms are used to launch multiple projectiles. For example, FIG. 5shows launch environment 500 with a first launch mechanism 502 and asecond launch mechanism 504. Various embodiments contemplate that afirst projectile 506 and a second projectile 508 may be supplied by adistribution system 510. Additionally or alternatively, variousembodiments contemplate at least portions of the first and secondprojectiles 506 and 508 connect in flight to form multiunit ATV 512, forexample, at 514. FIG. 5 also shows a portion of multiunit ATV 512transferring a resource from a portion of the first projectile to aportion of the second projectile. For example, the portion of the firstprojectile may transfer a kinetic energy boost to the portion of thesecond projectile, for example through a tether. Additionally oralternatively, after the portion of the first projectile has completedits transfer, it may separate from the portion of the second projectileand the portion of the second projectile 516 may continue, for example,complete orbit insertion, for example, at 518.

Additionally or alternatively, various embodiments contemplate that thepusher (e.g., obturator) may be magnetically propelled, or gaspropelled. For example, the interface to the projectile may look like 2obturators with a spring and damped between them. For example, duringthe initial start up transients and cold or hot gas pressuring push (ormagnetics) this pusher plate spring damper may offer the right dynamiccondition for G-sensitive payloads.

Additionally or alternatively, various embodiments contemplate the useof a magnet coupling with the ram accelerator projectile or obturator.For example, a non-metallic launch tube and ram accelerator pipe. Thenon ferrous materials would allow a magnetic field to pass between theram accelerator and the outside the tube, and speed up items in theatmosphere to (vacuum) that then mate or connect with other flyingsystems.

Additionally or alternatively, various embodiments contemplate that aconnection magnetically could create a great connection for precisematerial science applications.

Additionally or alternatively, various embodiments contemplate use ofdistributed cold gas injection for low G start. Additionally oralternatively, the system could use a Baffle Tube, railed tube or smoothbore projectile and ram acceleration system.

Additionally or alternatively, various embodiments contemplate that alaunch from a high altitude off a cliff may guarantee a safe recoverywith any velocity (including zero velocity) from ram accelerator. Thisembodiment may provide a simple Safe system allowing the vehicle andpayload (astronaut) to pull a drogue or parachute and safely land givenany positive energy state at the exit of the tube. For example, evenwith 0-velocity there is sufficient potential energy (height) andclearance at the top of the mountain or cliff to allow the capsuleparachute to pull.

Additionally or alternatively, various embodiments contemplate acollapsible cup, epplisoidal space vehicle may have a disk shape thatexpands like a F-11 ejection seat system.

Additionally or alternatively, various embodiments contemplate, a linearaerospike may be used. Additionally or alternatively, variousembodiments contemplate an annular aerospike may be embedded within aram accelerator projectile, for example, using a blunt end. Additionallyor alternatively, various embodiments contemplate using rotatingdetonation wave engine embedded in back of ram accelerator. Additionallyor alternatively, various embodiments contemplate using a ring shieldflying the ram accelerator then exiting and using an on-board propellantas a RAMAC-Air breathing RAM to Rocket system. For example, thisembodiment may be implemented as part of a whole or segmented,self-assembling system.

Additionally or alternatively, various embodiments contemplate using thesystem to deliver self-assembling satellites.

Additionally or alternatively, various embodiments contemplate beamedpower. For example, a ram projectile or a source in space may beamenergy to the ATV and run an electric based engine. Additionally oralternatively, various embodiments contemplate deploying a wide areasystem at altitude that can pump laser or electrical energy from orbitor from another projectile to the ATV. Additionally or alternatively,this approach may delay the degradation of the orbit insertion. Forexample, this lets the system fight gravity while the ATV is speeding upwith a lower impulse engine.

Additionally or alternatively, various embodiments contemplate deployinga balloon in one of these payloads, an Internet-connected app-store forspace, and/or storing fuel in the nose for use or delivery.

FIG. 6 shows multiple embodiments of launch system configurations. Forexample, FIG. 6 shows a launch system environment 600 where a firstlaunch system 602 comprising a ram accelerator launch system 604 iscoupled to a distribution system 608. Here, the distribution system 608is coupled to the ram accelerator launch system 604 through a loadingtube 610. Here, a projectile may travel from the distribution system608, through the loading tube 610 and be loaded into the ram acceleratorlaunch system 604 at or near the bottom of the launch tube, for example,at a start gun. Various embodiments contemplate this configuration to bea u-tube loader, a nested breech, or a breech loading system.

FIG. 6 also shows a second launch system 612 comprising ram acceleratorlaunch systems 614 and 616 coupled to a distribution system 618. Here,the distribution system 618 is coupled to the ram accelerator launchsystems 614 and 616 through a loading tube 620. Here, a projectile maytravel from the distribution system 618, through the loading tube 620and be loaded into either of the ram accelerator launch systems 614 or616. Here, the loader may insert the projectile at or near the bottom ofthe launch tube, at a point between the top and the bottom of the launchtube, or near the top.

FIG. 6 also shows third launch system 622 comprising a ram acceleratorlaunch system 624 coupled to a distribution system 628. Here, thedistribution system 628 is coupled to the ram accelerator launch system624 through a loading system 630. Here, a projectile may travel from thedistribution system 628, through the loading system 630 and be loadedinto the ram accelerator launch system 624 at or near the top of thelaunch tube. Various embodiments contemplate this configuration to be amuzzle loading system.

FIG. 7 shows an illustrative embodiment of projectile assembly 700. Forexample, FIG. 7 shows a payload module 702, an aero stabilizer structure704, an aeroshell 706, and an obturator 708. Various embodimentscontemplate that the payload module may be coupled to a nosecone 710.Additionally or alternatively, the aero stabilizer structure 704 maycomprise a telescoping or extending structure 712 to support and deployone or more aero stabilizing structures 714, for example fins, pulsecontrolled propulsion system (cold gas, chemical propulsion, etc).Additionally or alternatively, various embodiments contemplate that theaeroshell 706 may comprise one or more pieces 716 configured to houseand protect at least a portion of the payload module and aero stabilizerstructure. Various embodiments contemplate that the aeroshell 706 maydetach during flight to release the ATV.

FIGS. 8A-B show illustrative launch tube configurations. For example,FIG. 8A shows an illustrative cutaway of a baffle tube with a projectilewithin the baffle tube's bore. FIG. 8B shows an illustrative example ofdifferent projectiles moving through an illustrative baffle tubecutaways where illustrative shock waves are shown on each illustrativeprojectile.

FIG. 9 shows an illustrative launch system 900. Here, the launch system900 comprises a cold gas start system 902 coupled to a baffle ramaccelerator 904. Here, the cold gas start system 902 may have aninjection gas reservoir (not pictured) coupled to distributed high speedvalves. Here, FIG. 9 shows the high speed valves angled with respect tothe tube allowing for improved injection efficiency and momentumtransfer during injection.

FIG. 10 shows an illustrative distributed injection system 1000. Forexample, FIG. 10 shows a direction 1002 of a movement of a projectile1004. Here, highspeed valves or segmented pierce diagrams 1006 may beused to control the gas pressure. Arrow 1008 shows the illustrativedirection of the movement of gas from a reservoir through a nozzle ororifice at the injection point. Additionally, FIG. 10 shows supersonicor subsonic nozzles 1010. The configuration of nozzles may be selectedbased on the relative speed of the projectile 1004 as it passes eachnozzle.

FIGS. 11A-B show an illustrative ATV 1100. For example, FIG. 11A showsan illustrative ATV 1100 with a rocket vehicle encapsulate 1102. Here,for example, the rocket vehicle encapsulate 1102 may comprise 1, 2, 3,or more stages or may be part of a first, second, third, or beyondstages. FIG. 11A also shows an egg-crate support system 1104 configuredto support internal structures 1106 of the ATV.

FIG. 12 shows an illustrative locking system 1200 for a moveablediaphragm. For example, FIG. 12 shows a moveable diaphragm 1202 set in atube bore 1204. Here, the moveable diaphragm 1202 is locked into placeby a retractable member 1206, for example, a hydraulic piston.Additionally or alternatively, various embodiments contemplate usingdifferential pressures at either side of the moveable diaphragm 1202 tomove it into place in the tube bore 1204. Additionally or alternatively,a sealing mechanism, for example, O-ring 1208 may be disposed in themoveable diaphragm 1202 and may selectively seal against the inside ofthe tube bore 1204. Various embodiments contemplate applying a higherpressure to one side of the moveable diaphragm 1202, for example, at1210 when compared to the pressure at 1212. In this configuration, thehigher pressure at 1210 may cause a portion of the moveable diaphragm todisplace and cause the O-ring to press against the bore of the tube1204. When a sufficient pressure is applied, the O-ring may hold themoveable diaphragm 1202 in place while retractable member 1206 may beretracted from the tube bore 1204.

Illustrative Processes and Techniques

FIG. 13 shows an illustrative process and technique 1300 for launching aprojectile. For example, at 1302 a projectile is loaded into adistributed injection cold gas start gun of a ram accelerator.

At 1304, the system selectively pressurizes the tube of the cold gasstart gun to accelerate the projectile.

At 1306, the system releases a movable diaphragm towards the projectilein the cold gas start gun. This has the effect of increasing relativevelocity that the projectile experiences with respect to the gas andallows the projectile to reach effective ramming speed sooner than wouldotherwise be achievable.

At 1308, when the projectile nears the end of the cold gas gun, thesystem may open a fast-acting valve between the cold gas start gun and afirst ram section of the ram accelerator.

At 1310, the system passes the projectile through the fast-acting valvemaintaining a velocity of the projectile. The fast-acting valve allowsthe projectile to pass through the valve with minimal loss of effectivevelocity and allows any shock front associated with the projectile topass through the valve uninterrupted.

At 1312, the system accelerates the projectile through the ramaccelerator using ram combustion. The ram accelerator may have multiplestages using different gases tailored to the expected and desired speedof the projectile through each stage of the ram accelerator.

FIG. 14 shows an illustrative process and technique 1400 for launchingand connecting multiple projectiles. For example, at 1402, the systemmay launch a plurality of projectiles from a launch system. For example,multiple launch systems or technologies may be used to launch eachprojectile.

At 1404, the system may connect one projectile to one or more otherprojectiles. This may be accomplished by launching the projectiles onintercepting courses or through maneuvers of one or more projectilesafter launch. Various techniques and mechanisms may be used, forexample, thrusters, tethers, telescoping members, among others. Whensufficiently close to each other, the projectiles may more securely jointogether, for example, through the use of magnetic or physical lockingmechanisms.

At 1406, the connected projectiles, may transfer a resource from oneprojectile to another. For example, the transfer may comprise energy inthe form of electrical power, propellants, information, cargo, kineticenergy transfer, among others, or combinations thereof.

At 1408, the system may detach a projectile from the other projectile orprojectiles after the transfer. For example, if a propellant has beentransfer, the supplying projectile may be detached after the transfer.Additionally or alternatively, if a kinetic energy is transferred, forexample, through a tether, the pulling projectile (and in someembodiments the tether) may be detached after the pulling projectilecompletes the desired kinetic transfer.

Illustrative Tailorable Structure for Tailorable Higher-G Load OrbitalFlight

This disclosure also discloses a tailorable high acceleration resistantupper stage(s) structures for orbital insertion from a initial Ramaccelerated payload.

For example, based at least in part on a user-defined payload, forexample, shape (height, weight, length, curvature) and mass such as anano, micro satellite (Cubesat), moderate satellite, large satellite, orpayload (component launch, supply launch, among others, and the G-loadsallowable by that satellite, payload, and/or flight vehicle (Subsonic,supersonic or hypersonic) vehicle. The use may be used to set thedesired “Start” parameters of the encapsulated system. For example, thealtitude, velocity, and inclination that are desired or capable of beingprovided by the ram accelerator or multiple ram accelerator systems fora multi-vehicle swarm, in-flight self-assembling launch system.

The Ram accelerator system may be defined or configured using variousfactors, including, for example, but not limited to, the overall lengthand stage lengths may be based on the respective gas mixture typesavailable, fill pressure delivery, and maximum dynamic pressure pulsecapability (e.g., detention, deflagration, and ram accelerator normal20× Pressure spike operations). The system, for example, a ramaccelerator analysis computer, may determine a predicted G-loadingprofile of the Ram accelerator (ATV) atmospheric transit vehicle as afunction of time (milliseconds typically) and as a function of travelalong the tube. The ram accelerator analysis computer programs may thendetermine the maximum dynamic “G” loads the ATV and thus any bodies thatare encapsulated in the ATV will experience. Based on the aboveinformation and the Geometry, (Diameters, length, mass) of the Ramaccelerator(s) one or more for multi-simultaneous or near simultaneousoperations, the system may also determine the reaction loads imparted onthe holding structure of the ram accelerator tubes. The holdingstructures may be mass, gas springs and dampers connected to a varietyof structures and at inclination of such vehicles as high altitudeaircraft (cargo 747, etc) or barge or boat, ship, rail car, or contactwith the ground or underground drill site, drill rigs or miningequipment as non-limiting examples.

Additionally or alternatively, various embodiments contemplate that asthe Gas start gun, the launch tube and the Ram accelerator all impart avariety of loading conditions and end-state conditions (e.g., velocityof the tube, atmospheric transit times, maximum expected loftedaltitude). Here, the system may assess the conditions and define arequired Delta V (velocity requirement from the rocket equation) foreach stage. Based on propellant types and mixtures and engines thesystem will compute tank requirements for the system and estimatestructural tank sizing based on the ram accelerator(s) loads predictedsizing wall thickness for hydrostatic and shock load pressurization andload sharing. The following process follows the multiple computer codesused to generate the optimized light weight structure. The one of thenotable features of the disclosed technique is the carrying of theoptimized structure via a fluid ballast inside the atmospheric transitvehicle fairing. Which may be represented by a cylindrical or optimallyformed (shaped pressure vessel).

Additionally or alternatively, various embodiments contemplate that thesystem may start with payload requirements, for example, 20 kg, 450 km,500 G maximum. The system may determine ram requirements, for example,inclination, exit elevation, delta V splits (ram stage, stage 2, . . .stage n), and may apply a top-down gross orbital analysis. The systemmay also determine the propulsion system requirements, for example, themass, the thrust, and the specific impulse (ISP). The system may thenperform a tank and structural design, for example, determining volume,the G-load maximum, the wall thickness, the structural mass. The systemmay then determine ram tube and ATV design, for example, determining theexpected G's, pressure, gases/propulsion medium, lengths, number ofstages, tube diameter, wall thickness, and ATV design, for example,determining and/or resolving structural interferences with the otherdetermined factors/constraints. The system may then determine thethermal requirements, for example, determining the configuration of thenose, body, fin and related materials, as well as the expectedtemperatures, the encapsulation design, the in-tube atmosphere, the exitatmosphere, the down range atmosphere, and/or heating loads.

Additionally or alternatively, the system may then model the system by,for example, integrating the structures and loads models, for example,by integrating and evaluating the models in computer aided drafting(CAD) and/or analysis systems (e.g., finite element (FE) or finiteanalysis (FA)). The system may determine loads, for example, structuraland/or thermal, and compare the analysis against failure criteria. Thesystem may also perform aerodynamic and/or stability analysis, forexample, determine the coefficient of drag (Cd) and stability factors(e.g., CM-alpha). The system may then determine orbital or flightperformance, for example, burn duration, required thrust, hang-time,circularization, as well as GN&S, RCS, and avionics requirements.Further, the system may determine stability and control in the variouslevels of atmosphere including various orbit distances as well aspayload separation. Here, the system may determine whether the designedsystem is possible, for example, determine whether the design is closed.If the system determines that the requirements are not met, then thedesign is not closed, and the system may return to an earlier part ofthe analysis and iterate the design, for example, by returning todetermining the ram requirements. If the system determines that thedesign is closed, then the system may provide a launch vehicle andaccelerator design, for example, mass properties, geometries,performance margins, modular designs, and/or a bill of materials. Thesystem may use this design and determine cost and operation models, forexample, the ram accelerator capital expenses and operational expensesand/or the N-stage orbital vehicle costs and/or manufacturing lead time.

Additionally or alternatively, since a system for a nano, micro andsmall sat systems with initial velocity and/or altitude provided by theram accelerator boosted stage 1 launch, are typically much smaller thantoday's larger conventional Vertical take off (0 velocity) rockets, theoverall system tank sizes and transport elements, instrumentation andinsulation requirements are much easier and smaller for the same payloadto orbit. As such, various embodiments contemplate that the system mayuse a “blow down” system (or rotationally or piston pumped) rocketpropellant (fuel and oxidizer systems). For example, for a blow-downsystem, the entire system may be developed as nearly a single, customdesign for each flight or replicated for multiple flights.

Additionally or alternately, the ATV may be built in multiple parts. Forexample, the ATV “fairing” may be filled with a fluid that providesbuoyancy to the system and/or system components such as fuel or oxidizertanks. The fluid provides the force or load transmission similar to butmore efficient as a “continuous” structure load transmission element.The fluid component may be used additionally as center of gravitymodifier or ballasting as a manner of G loading from acceleration in thetube or differential loading to move (via physics or pressure pumptransfer for automated transfer) the ballast to moves the center ofgravity during high drag out of tube. In the tube the CG (center ofgravity) is preferentially aft for ram acceleration in-tube, butpreferentially forward during atmospheric transit forward. The fluidballast (fluid, various density, ballasted shot, etc) may be movedforward after exit from the tube.

One embodiment of the construction and manufacturing of the stages maybe through the use of a central common transport elementing line made ofsingle or multiple segments with various pathways through themconnecting the pressurization tank to the oxidizer and fuel tanks alongwith wiring and sensors that are pre-placed on inflated or thing metaltanks. As a rough though approximation, the system may be configured tohave a central line or lines, reminiscent of a shish-kabob, where thecentral line(s) may include fluid, pressure and mechanical components,with various diaphragms set to break at specific pressure conditions(plugs) or pyro activated, etc that allows the pressure to flow and thenthat pressure flows to the ullage locations in the oxidizer and fueltanks respectively the fluids then mix at the engine and provide thrustfor the craft. The system may be automatically manufactured in whole orin-part with 3D manufacturing techniques using metal, plastics, and/orcomposites.

FIGS. 15 and 16 show an illustrative embodiment of this configuration.For example, FIG. 15 shows an ATV 1500 that includes a ram fairing 1502,for example a ram accelerator shaped fairing. The ATV 1500 may have aballast cavity 1504 that may be filled with a ballast medium 1506. Theballast medium 1506 may apply a buoyancy force 1508 to payload system1510. Payload system 1510 may include a propulsion system 1512, forexample, a rocket motor 1514. The propulsion system 1512 may include anoxidizer tank 1516 coupled to the rocket motor 1514, for example throughan ox conduit/pipe 1518. FIG. 15 also shows a fuel tank 1520 coupled torocket motor 1514, for example, through fuel conduit/pipe 1522. Variousembodiments contemplate that the fuel conduit/pipe 1522 may pass throughor around oxidizer tank 1516. Additionally or alternatively variousembodiments contemplate that propulsion system 1512 may include apressurization tank 1524 that may be coupled to the oxidizer tank 1516and/or the fuel tank 1520 and may apply a pressure through a pressuregas path 1526, for example, helium, N2, among others. Additionally oralternatively various embodiments contemplate that propulsion system1512 may include an oxidizer blowdown plug/diaphragm 1528 and/or a fuelblowdown plug/diaphragm 1530 coupled to the oxidizer tank 1516 and thefuel tank 1520 respectively. Additionally or alternatively, the ATV 1500may include an ATV fairing 1532. Various embodiments contemplate thatATV fairing 1532 may include variable configurations including, forexample, in shape, in density, buoyancy, and/or ballast. For example,the ATV fairing 1532 may include liquid, foam, or morphing materials toact as a ballast and/or provide buoyancy forces to the payload system1510.

Additionally or alternatively, various embodiments contemplate that theloads during the Ram accelerator launch may be the largest loads thesystem may likely see and the fluid or fluid-like ballast (foam) etcthat are in the ATV fairing provides a buoyancy force to the tanks toallow the tanks and the fluid in them to see very low loads, allowingfor this effectively central, line lowly supported structure. However,some embodiments contemplate a need for additional structural support orconformal tank manufacturing to be more efficient with loading. Thisfeature, however, is very powerful in creating an easy to manufactureand light weight structure for orbital insertion while the ATVatmospheric in-flight structure already needs to be heavy enough toprovide the momentum and limit the atmospheric drag loss (and CGrequirements) during the flight.

A fiberglass, composite, metallic, and/or 3D printed material may coatover the top of the tanks or be co-manufactured to make a nearlymonocoque construction for the upper stage insertion vehicle.

Additionally or alternatively, various embodiments contemplate thatsystem, or portions thereof, may be rapidly manufactured, for example,3D printed in metal, composite, plastics, or combinations thereof. Forexample, since the system may identify a unique configuration, rapidmanufacturing techniques may be used to build the specified system. Forexample, three dimensional printing (3D printing) may be used to createsome or all the components. The 3D printing may be a single material ormay use multiple materials. For example, the 3D printer may use a metalbased material, a plastic based material, a ceramic based material,composite materials, or combinations thereof. Additionally oralternatively, the system may use additive manufacturing techniques, forexample, 3D printing or subtractive manufacturing techniques, forexample, computer numerical controlled (CNC) machining processes.

FIG. 16 shows a payload preparation system 1600 with payload system 1602similar to payload system 1510 shown in FIG. 15. Here, payload system1602 may be supported by support structure 1604. As discussed above,support structure 1604 may include various materials, and may bedesigned based at least in part on the expected G-loading and supportprovided by a buoyancy force, if present.

FIG. 17 shows an illustrative ball valve system 1700 where ball valve1702 may operate within a ram tube 1704. The ball valve 1702 may benominal slow or high speed (for example, 1-10 millisecond opening time).Additionally or alternatively, the ball valve 1702 may selectivelyseparate a first portion 1706 of the ram tube 1704 from a second portion1708 of the ram tube 1704. Ball valve 1702 may include an orifice 1710configured to allow a projectile to pass through when positioned in anopen position, and prevent pressure or a projectile to pass between ramtube portions in a closed position.

The ball valves in entrance and exit stages may be high speed to create“shutter-like” window-opening timeframe allowing the projectile to enterand exit nearly instantaneously as the projectile is arriving. Theintermediate ball valves may be used to separate the parallel orsequential filling of each ram accelerator or baffle tube ramaccelerator stages of gases. Prior to initiation of ram acceleratorstart (e.g., centrifugal, start gun, etc) the intermediate ball valvemay operate and be opened for flight through the ram accelerator tubes.In various embodiments, the timing of the intermediate valve is not ascritical as the opening and exit valves, such that while it is notrequired to operate on millisecond timeframe for “shutter-like”operation, it operates in a timeframe that limit the amount of naturalconvective mixing between gas stages allowing intermediate ramaccelerator stages of various fuel, oxidizer and inter gases (for soundspeed tailoring) allowing the passage of the ram accelerator projectilesas if it is separated by a physical diaphragm.

Illustrative Operational Environments

Additionally or alternatively, various embodiments contemplate that theram acceleration system may be located on a mobile platform includingland based drilling rig, or water borne platforms such as a barge or aship. This provides the ability for optimal launching for a givenmission.

FIGS. 18A-D show an illustrative embodiment of a launch system 1800coupled to an aircraft 1802. Various embodiments contemplate that thelaunch system 1800 may include one or more ram launch tubes 1804configured to launch a projectile from an operating altitude of aircraft1802. This launch system may have some or all the features describedabove and/or below.

FIG. 19 shows an illustrative launch system 1900. In this embodiment,the launch system 1900 includes a kinetic start system 1902 coupled tothe ram acceleration portion 1904. For example, the kinetic start system1902 includes a centrifugal launch configuration, where for example, apayload 1906 is accelerated to an initial ram velocity through aspinning action. The kinetic start system may spin the payload 1906 andgradually accelerate the payload 1906 to an initial ram velocity overthe course of multiple revolutions. Additionally or alternatively,various embodiments contemplate that the kinetic start system 1902 mayinclude multiple start systems. For example, a spinning kinetic startportion may be used to accelerate the payload 1906 to a first velocity,and a second stage, for example, a cold gas gun or pressurization systemmay accelerate the payload 1906 from the first velocity to a secondvelocity, where the first velocity may be below an initial ram velocityand the second velocity may be above the initial ram velocity. Variousembodiments contemplate that more than two stages or configurations maybe used to bring the payload 1906 up to the initial ram velocity.

Additionally or alternatively, various embodiments contemplate thatmultiple launch systems may be used, for example multiple ram tubes, tolaunch multiple projectiles simultaneously or within a time period ofeach other. Additionally or alternatively, various embodimentscontemplate that the multiple launch systems may use the same startsystem, for example kinetic start system or different start systems, orcombinations thereof, based at least in part on the payload, desiredmission profile, proximity of launch systems, and/or availability oflaunch systems, among others.

FIG. 20 shows an illustrative launch system 2000. For example, launchsystem 2000 may include a start system 2002 and a ram tube 2004. Thestart system 2002 may include various acceleration configurations toaccelerate a projectile 2006 to a start speed before exiting the startsystem 2002. For example, the start system 2002 may include a kineticstart system, for example, a rotary kinetic launcher, a gas gun,sequenced gas impulses (e.g., cold or hot gases or combustible gases),among others, or combinations thereof. Additionally or alternatively,the ram tube 2004 may comprise multiple sections holding selectedmixtures of propellant components as discussed in this disclosure wherethe multiple sections may be isolated from each other by varioustechniques, for example, ball valves, fast valves (ball, gate, etc),burst discs, diaphragms, among others, or combinations thereof.

Additionally or alternatively, various embodiments contemplate that theprojectile 2006 may disperse fuel from selected portions, for example,the nose cone 2008 and/or side walls 2010. In this embodiment, theemitted fuel may mix (e.g., combine and/or atomize) with oxidizers 2012in the tube or oxidizers 2014 present out of the tube. This embodimentprovides a unique feature that may allow the launcher to be used withoutpremixing detonable mixtures in the tube. This may allow for a safer andpossibly faster launch prep when compared to introducing premixedcombustibles into the tube.

Additionally or alternatively, various embodiments contemplate that theprojectile 2006 may include a shroud 2016. For example, shroud 2016 mayallow gases present in the ram tube 2004 to pass through the shroud 2016and around a main body of the projectile 2006. In this configuration,the shroud 2016 may act as the wall of the ram tube 2004 to maintain thepressures of the gasses and combustion behind the shock wave 2018.

Additionally or alternatively the launch system 2000 may include anobturator 2020. For example, the obturator 2020 may be configured tomove behind projectile 2006 through the ram tube 2004 to aid inpropelling the projectile 2006 through the ram tube 2004 by increasingthe desirable pressure difference between the gasses ahead of theprojectile 2006 and the combustion projects and gasses behind theprojectile 2006. When the projectile 2006 leaves the ram tube 2004various embodiments contemplate that the obturator 2020 may decoupleand/or fall away from the projectile 2006.

Additionally or alternatively, various embodiments contemplate that whenthe projectile 2006 operates in the tube or leaves the ram tube 2004,the projectile 2006 may begin and/or continue to disperse fuel fromselected portions of the projectile causing the fuel to mix with theoxidizers 2014 and provide ramjet thrust/combustion 2022 to propel theprojectile 2006.

Additionally or alternatively, various embodiments contemplate that theshroud 2016 may be adjustable with respect to the nose cone 2008 and/orthe nose cone 2008 may be adjustable with respect to the shroud 2016 tooptimize or improve the ram combustion for the changes in velocity andaltitude density. For example, the nose cone 2008 and/or the shroud 2016may be adjusted with respect to each other to allow the shock wave 2018to interact with the shroud 2016 to more effectively utilize the ramcompression caused by the shock wave 2018.

Additionally or alternatively, various embodiments contemplate that aram tube may not be needed or a relatively short ram tube may be used,where the projectile may be accelerated to a ram velocity throughvarious start techniques, for example, kinetic starts including a rotarykinetic launcher, a gas gun, sequenced gas impulses, among others, orcombinations thereof. Upon release, the projectile may have sufficientvelocity to maintain a ram acceleration through the airbreathing ram jetconfiguration.

Additionally or alternatively, various embodiments contemplate that theprojectile 2006 may have collapsible and/or deployable fins. Forexample, while the projectile 2006 is in the tube, the fins may becollapsed and/or stowed. To help keep the projectile 2006 stable varioustechniques may be used. For example, the projectile may be spinstabilized and/or guided by a rail and/or spacers. Further, variousembodiments contemplate that the projectile 2006 may be spin stabilizedafter leaving the ram tube 2004. Additionally or alternatively, fins maybe deployed after the projectile 2006 has left the ram tube 2004 toprovide stabilization. Additionally or alternatively, combinations ofboth fins and spin stabilization techniques may be used together.

Various embodiments contemplate a start gun system for accelerating aprojectile to ram speed comprising: a distributed injection system thatincludes a start tube configured to selectively inject a pressurant, anda control system configured to control staged injection of thepressurant along the start tube, as well as a movable diaphragmconfigured to increase the relative velocity of the projectile in amedium. For example, the movable diaphragm is configured to move towardsthe projectile through the start tube. Further, the selective injectionof the pressurant may include injection into the start gun tube throughone or more of gas baffles, high speed valves, or diaphragms.

The gas baffles may represent baffle tube ram accelerator, where eachvolume of the baffle offers high energy propellant for projectileacceleration and limiting the capability of the gases to gas-dynamicallyunstart and stop or slow the ram acceleration process. The pressurantmay be distributed through high speed injection valves (e.g., ballvalves, pintle, solenoid, etc) inert gas (nitrogen, helium) or anoxidizer (air, Oxygen, etc) or a combustible gas such as dieselair/methane air with distributed spark ignition, among others.

Additionally or alternatively, the start gun system may include anonsite distribution system configured to, upon request of a user, selectand load into the start gun system a projectile, and launch the selectedand loaded projectile. Additionally or alternatively, the start gunsystem may include a ram accelerator coupled to the distributedinjection system and the moveable diaphragm, wherein the ram acceleratoris disposed in an underground facility, a floating system, or a flyingvehicle.

Additionally or alternatively, various embodiments contemplate amultiple projectile launch system comprising a plurality of launchmechanisms configured to accelerate a respective projectile each, afirst control system configured to coordinate the acceleration of therespective projectiles in the respective plurality of launch mechanisms,and a second control system, disposed in one or more of the respectiveprojectiles, configured to assemble one or more of the respectiveprojectiles in flight after launch.

For example, the plurality of launch mechanisms may include one or moreof a ram accelerator, a kinetic energy launch system, a hybrid launchsystem, a chemical rocket system, an electric propulsion launch system,or combinations thereof. Additionally or alternatively, the firstcontrol system may be configured to stage a first projectile from afirst system and a second projectile in a second system such that thefirst projectile in the first system experiences a lower g-load than thesecond projectile in the second system.

Additionally or alternatively, one or more of the respective projectilesincludes one or more of a tether system, a locking mechanism, apropellant transfer system, or combinations thereof, and the secondcontrol system is configured to activate the one or more of the tethersystem, the locking mechanism, the propellant transfer system, orcombinations thereof to act on at least one other of the respectiveprojectiles.

Additionally or alternatively, the multiple projectile launch system mayalso include an onsite distribution system configured to, upon requestof a user, select and load into two or more of the plurality of launchmechanisms two or more projectiles, and launch the selected and loadedtwo or more projectiles.

Additionally or alternatively, various embodiments contemplate atechnique of self-assembly of projectiles, including launching aplurality of projectiles from a launch system, causing one or more ofthe plurality of projectiles to connect to one or more other projectilesof the plurality of projectiles, and transferring one or more of aforce, energy, or payload from one of the plurality of projectiles toone or more other projectiles for the plurality of projectiles. Forexample, the connection includes a tether between a first projectile ofthe plurality of projectiles and a second projectile of the plurality ofprojectiles, and the first projectile transfers a force to the secondprojectile through the tether.

Additionally or alternatively, the technique may include detaching oneor more of the connected projectiles from another projectile of theplurality of projectiles after the transferring.

Further, the disclosure contemplate a system for launching payload asdescribed above. Further still, the disclosure contemplates a systemcomprising a launcher and a payload loading system, wherein the launcheris configured to accelerate a payload along a tube.

CONCLUSION

Although embodiments have been described in language specific tostructural features and/or methodological acts, it is to be understoodthat the disclosure is not necessarily limited to the specific featuresor acts described. Rather, the specific features and acts are disclosedherein as illustrative forms of implementing the embodiments. Anyportion of one embodiment may be used in combination with any portion ofa second embodiment.

What is claimed is:
 1. A start gun system for accelerating a projectile to ram speed comprising: a distributed injection system comprising: a start tube configured to selectively inject a pressurant; a control system configured to control staged injection of the pressurant along the start tube; and a movable diaphragm configured to increase a relative velocity of the projectile in a medium.
 2. The start gun system of claim 1, wherein the movable diaphragm is configured to move towards the projectile through the start tube.
 3. The start gun system of claim 1, wherein the selective injection of the pressurant comprises injection into the start gun tube through one or more of gas baffles, high speed valves, or diaphragms.
 4. The start gun system of claim 1, further comprising an onsite distribution system configured to, upon request of a user, select and load into the start gun system, a projectile, and launch the selected and loaded projectile.
 5. The start gun system of claim 1, further comprising a ram accelerator coupled to the distributed injection system and the moveable diaphragm, wherein the ram accelerator is disposed in an underground facility, a floating system, or a flying vehicle.
 6. A multiple projectile launch system comprising: a plurality of launch mechanisms configured to accelerate a respective projectile each; a first control system configured to coordinate the acceleration of the respective projectiles in the respective plurality of launch mechanisms; and a second control system, disposed in one or more of the respective projectiles, configured to assemble one or more of the respective projectiles in flight after launch.
 7. The multiple projectile launch system of claim 6, wherein the plurality of launch mechanisms comprises one or more of a ram accelerator, a kinetic energy launch system, a hybrid launch system, a chemical rocket system, an electric propulsion launch system, or combinations thereof.
 8. The multiple projectile launch system of claim 6, wherein the first control system configured to stage a first projectile from a first system and a second projectile in a second system such that the first projectile in the first system experiences a lower g-load than the second projectile in the second system.
 9. The multiple projectile launch system of claim 6, wherein one or more of the respective projectiles comprises one or more of a tether system, a locking mechanism, a propellant transfer system, or combinations thereof; and the second control system is configured to activate the one or more of the tether system, the locking mechanism, the propellant transfer system, or combinations thereof to act on at least one other of the respective projectiles.
 10. The multiple projectile launch system of claim 6, further comprising an onsite distribution system configured to, upon request of a user, select and load into two or more of the plurality of launch mechanisms two or more projectiles, and launch the selected and loaded two or more projectiles.
 11. A method of self-assembly of projectiles, the steps comprising: launching a plurality of projectiles from a launch system; causing one or more of the plurality of projectiles to connect to one or more other projectiles of the plurality of projectiles; and transferring one or more of a force, energy, or payload from one of the plurality of projectiles to one or more other projectiles for the plurality of projectiles.
 12. The method of claim 11, wherein the connection comprises a tether between a first projectile of the plurality of projectiles and a second projectile of the plurality of projectiles; and the first projectile transfers a force to the second projectile through the tether.
 13. The method of claim 11, further comprising: detaching one or more of the connected projectiles from another projectile of the plurality of projectiles after the transferring. 